15x7 (15x7.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 1.2500 -7.8960 0.0000 0.0000 0.6250 0.0000 0.3481 0.0000 0.4351 0.0000 0.1500 0.0000 0.0000 0.1800 1.2001 -6.0424 0.0117 -0.5416 0.6179 0.0069 0.3293 0.5909 0.3952 0.4555 0.1558 0.0144 -0.0637 0.3600 1.1588 -4.3118 0.0904 -1.0311 0.6143 0.0254 0.3113 2.2889 0.3608 0.4434 0.1709 0.0329 -0.0538 0.5400 1.1271 -2.7044 0.2929 -1.3496 0.6139 0.0524 0.2943 4.9336 0.3317 0.4252 0.1922 0.0532 -0.0400 0.7200 1.1061 -1.2202 0.6584 -1.4054 0.6164 0.0848 0.2782 8.2812 0.3077 0.4025 0.2174 0.0746 -0.0236 0.9000 1.0965 0.1410 1.2045 -1.1467 0.6214 0.1197 0.2629 12.0244 0.2883 0.3771 0.2441 0.0969 -0.0059 1.0800 1.0974 1.3790 1.9232 -0.5685 0.6285 0.1541 0.2486 15.8234 0.2728 0.3506 0.2700 0.1194 0.0119 1.2600 1.1068 2.4940 2.7802 0.2842 0.6376 0.1850 0.2351 19.3500 0.2602 0.3244 0.2924 0.1418 0.0279 1.4400 1.1214 3.4858 3.7149 1.3159 0.6482 0.2096 0.2225 22.3224 0.2495 0.2996 0.3086 0.1631 0.0401 1.6200 1.1368 4.3544 4.6424 2.3829 0.6599 0.2248 0.2108 24.5172 0.2397 0.2776 0.3154 0.1822 0.0459 1.8000 1.1489 5.1000 5.4562 3.2987 0.6726 0.2276 0.2000 25.7543 0.2298 0.2596 0.3100 0.1974 0.0419 1.9799 1.1575 5.7220 6.0986 4.0163 0.6859 0.2208 0.1901 26.1163 0.2201 0.2444 0.2959 0.2086 0.0319 2.1574 1.1666 6.2155 6.6094 4.6723 0.6995 0.2120 0.1812 25.9929 0.2114 0.2298 0.2819 0.2181 0.0240 2.3348 1.1760 6.5889 6.9981 5.2520 0.7135 0.2018 0.1732 25.5026 0.2036 0.2159 0.2677 0.2265 0.0178 2.5122 1.1854 6.8427 7.2658 5.7342 0.7276 0.1902 0.1660 24.7166 0.1968 0.2032 0.2536 0.2339 0.0129 2.6897 1.1944 6.9769 7.4129 6.1004 0.7415 0.1776 0.1597 23.6843 0.1907 0.1918 0.2393 0.2405 0.0090 2.8671 1.2029 7.0000 7.4487 6.3431 0.7550 0.1639 0.1542 22.4645 0.1855 0.1819 0.2250 0.2465 0.0058 3.0445 1.2104 7.0000 7.4624 6.5331 0.7679 0.1497 0.1497 21.3111 0.1811 0.1736 0.2107 0.2528 0.0016 3.2219 1.2167 7.0000 7.4777 6.6907 0.7799 0.1352 0.1459 20.2733 0.1776 0.1669 0.1962 0.2592 -0.0038 3.3993 1.2214 7.0000 7.4952 6.8159 0.7908 0.1203 0.1431 19.3371 0.1748 0.1617 0.1818 0.2657 -0.0104 3.5767 1.2245 7.0000 7.5154 6.9088 0.8004 0.1050 0.1411 18.4907 0.1728 0.1580 0.1672 0.2720 -0.0180 3.7541 1.2254 7.0000 7.5387 6.9693 0.8084 0.0891 0.1400 17.7240 0.1715 0.1555 0.1526 0.2781 -0.0266 3.9316 1.2240 7.0000 7.5638 6.9977 0.8146 0.0732 0.1393 17.0242 0.1705 0.1536 0.1380 0.2837 -0.0359 4.1090 1.2200 7.0000 7.5887 7.0000 0.8187 0.0574 0.1386 16.3800 0.1691 0.1517 0.1232 0.2887 -0.0455 4.2864 1.2131 7.0000 7.6135 7.0000 0.8206 0.0418 0.1379 15.7851 0.1672 0.1491 0.1084 0.2929 -0.0552 4.4638 1.2030 7.0000 7.6380 7.0001 0.8200 0.0265 0.1371 15.2340 0.1650 0.1458 0.0936 0.2960 -0.0650 4.6412 1.1893 7.0000 7.6623 7.0001 0.8166 0.0114 0.1364 14.7219 0.1623 0.1417 0.0787 0.2980 -0.0746 4.8186 1.1719 7.0000 7.6862 7.0000 0.8102 -0.0035 0.1357 14.2446 0.1591 0.1368 0.0637 0.2988 -0.0842 4.9960 1.1505 7.0000 7.7095 7.0000 0.8007 -0.0181 0.1350 13.7984 0.1553 0.1311 0.0487 0.2981 -0.0936 5.1734 1.1246 7.0000 7.7321 7.0000 0.7876 -0.0324 0.1343 13.3803 0.1510 0.1246 0.0336 0.2960 -0.1029 5.3509 1.0942 7.0000 7.7541 7.0000 0.7709 -0.0464 0.1336 12.9874 0.1462 0.1173 0.0184 0.2922 -0.1119 5.5283 1.0588 7.0000 7.7752 7.0000 0.7502 -0.0601 0.1329 12.6172 0.1407 0.1092 0.0032 0.2867 -0.1208 5.7057 1.0181 7.0000 7.7952 7.0000 0.7254 -0.0735 0.1322 12.2674 0.1346 0.1005 -0.0121 0.2793 -0.1293 5.8831 0.9720 7.0000 7.8140 7.0000 0.6961 -0.0865 0.1315 11.9361 0.1278 0.0911 -0.0274 0.2700 -0.1376 6.0605 0.9201 7.0000 7.8312 7.0000 0.6622 -0.0991 0.1308 11.6212 0.1203 0.0812 -0.0428 0.2585 -0.1455 6.2379 0.8621 7.0000 7.8464 7.0000 0.6235 -0.1113 0.1300 11.3207 0.1121 0.0709 -0.0583 0.2448 -0.1531 6.4153 0.7977 7.0000 7.8590 7.0000 0.5796 -0.1232 0.1293 11.0326 0.1032 0.0605 -0.0738 0.2289 -0.1604 6.5928 0.7267 7.0000 7.8680 7.0000 0.5304 -0.1346 0.1286 10.7546 0.0935 0.0500 -0.0894 0.2105 -0.1672 6.7702 0.6487 7.0000 7.8728 6.9992 0.4757 -0.1456 0.1279 10.4855 0.0830 0.0397 -0.1051 0.1895 -0.1736 6.9476 0.5638 7.0000 8.0270 6.9327 0.4151 -0.1541 0.1272 10.4193 0.0717 0.0298 -0.1203 0.1659 -0.1797 7.1177 0.4759 7.0000 8.4814 6.8372 0.3513 -0.1592 0.1265 10.7385 0.0602 0.0211 -0.1339 0.1406 -0.1848 7.1629 0.4514 7.0000 8.6637 6.8187 0.3334 -0.1602 0.1263 10.8963 0.0570 0.0190 -0.1372 0.1335 -0.1860 7.2008 0.4305 7.0000 8.8384 6.8080 0.3181 -0.1610 0.1262 11.0536 0.0543 0.0172 -0.1400 0.1274 -0.1869 7.2386 0.4092 6.9826 9.0161 6.7855 0.3024 -0.1617 0.1260 11.2127 0.0516 0.0156 -0.1427 0.1211 -0.1878 7.2765 0.3875 6.9317 9.1809 6.7361 0.2865 -0.1626 0.1259 11.3545 0.0488 0.0139 -0.1454 0.1147 -0.1885 7.3144 0.3652 6.8473 9.3471 6.6594 0.2700 -0.1634 0.1257 11.4962 0.0459 0.0124 -0.1481 0.1079 -0.1891 7.3523 0.3370 6.7294 9.4886 6.5625 0.2479 -0.1656 0.1256 11.6071 0.0423 0.0105 -0.1522 0.0982 -0.1905 7.3902 0.2991 6.5780 9.6168 6.4824 0.2163 -0.1698 0.1254 11.7010 0.0375 0.0083 -0.1586 0.0832 -0.1929 7.4280 0.2455 6.3932 9.7300 6.4567 0.1695 -0.1773 0.1253 11.7762 0.0308 0.0056 -0.1686 0.0598 -0.1972 7.4659 0.1480 6.1748 9.8272 6.8684 0.0799 -0.1940 0.1251 11.8319 0.0185 0.0021 -0.1890 0.0129 -0.2066 7.5000 0.0124 5.9497 5.9498 5.9496 -0.0474 -0.2201 0.1250 7.1960 0.0016 0.0000 -0.2202 0.0000 0.0000 RADIUS: 7.50 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 1.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.171764 TOTAL WEIGHT (Kg) = 0.077897 TOTAL VOLUME (IN**3) = 2.798253 TOTAL PROJECTED AREA (IN**2) = 15.0268 MOMENT OF INERTIA (SNAIL-IN**2) = 0.004103 MOMENT OF INERTIA (Kg-M**2) = 0.000463 STATIC MOMENT, ONE SIDE (IN-LB) = 0.206367 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 84.620 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11671.54 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.